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针对双自由度二元机翼,利用准定常气动力建立了非线性气动弹性方程,并以状态空间形式描述.双控制面非线性气动弹性系统中前后缘控制量相互耦合,不能直接应用反演自适应控制方法,为了解决这一问题,新定义了两个等效控制器.考虑俯仰方向立方非线性参数未知,根据Lyapunov稳定性理论设计了反演自适应控制律.通过Runge-Kutta数值方法对气动弹性方程进行求解,验证了控制律的有效性.仿真结果表明:所设计的控制器能够使开环不稳定的气动弹性系统稳定至零点,双控制面的作用提高了颤振临界速度.考虑到实际控制面的偏转限制,研究了单控制面失效问题,结果显示单后缘控制面比单前缘控制面对系统控制更有效.
For a two-degree-of-freedom binary wing, a nonlinear aeroelastic equation is established by quasi-steady aerodynamics and described in the form of state space. The forward and backward control quantities in a dual control plane nonlinear aeroelastic system are mutually coupled and can not be directly applied to inversion In order to solve this problem, two equivalent controllers are newly defined.According to Lyapunov stability theory, an adaptive inversion control law is proposed, considering that the cubic nonlinear parameters of pitch direction are unknown.According to the Runge-Kutta numerical method The effectiveness of the control law is verified by solving the aeroelasticity equation.The simulation results show that the designed controller can stabilize the aeroelastic system with open-loop instability to zero, and the double control surface can improve the flutter critical speed. Considering the deflection limitation of the actual control plane, the problem of single control plane failure is studied. The results show that the single trailing edge control plane is more effective than the single-limbs control system control.